阅读说明：本技术 一种兼顾跨、超声速气动性能的飞机 (Aircraft with cross-over supersonic pneumatic performance ) 是由 袁兵 魏中成 曹硕 喻岩 曹原 于 2020-12-04 设计创作，主要内容包括：本发明属于飞行器设计技术,涉及一种兼顾跨、超声速气动性能的飞行器布局飞机。所述机身头部为细长尖头状,机翼采用中等后掠角梯形机翼,机身后端两侧对称安装全动平尾,机身后端上方安装一个大后掠垂尾,垂尾后端安装方向舵,飞机的发动机进气道位于机身中前部两侧,飞机的发动机舱位于机身尾部；其中机身长细比为8-11,机翼前缘后掠角为35°-45°,平尾的前缘后掠角为35°-45°,垂尾的前缘后掠角为50°-60°。本发明所公开的飞机气动布局在保证飞机亚声速可控性基础上,实现了跨声速和超声速的升阻比最大化,还能够满足从亚声速到超声速横航向的稳定控制。(The invention belongs to the aircraft design technology, and relates to an aircraft layout aircraft with both span and supersonic aerodynamic performance. The aircraft comprises an aircraft body, a front end, a rear end, a tail, a rudder, engine air inlet channels of the aircraft, engine cabins of the aircraft and a tail end, wherein the head of the aircraft body is in a slender pointed shape, the wings are trapezoidal wings with medium sweepback angles, full-motion horizontal tails are symmetrically arranged on two sides of the rear end of the aircraft body, a large sweepback vertical tail is arranged above the rear end of the aircraft body, the rear; wherein the slenderness ratio of the fuselage is 8-11, the sweep angle of the front edge of the wing is 35-45 degrees, the sweep angle of the front edge of the horizontal tail is 35-45 degrees, and the sweep angle of the front edge of the vertical tail is 50-60 degrees. The aerodynamic layout of the airplane disclosed by the invention realizes the maximization of the lift-drag ratio of transonic speed and supersonic speed on the basis of ensuring the subsonic speed controllability of the airplane, and can also meet the stable control from subsonic speed to supersonic speed in the horizontal course.)

1. An aircraft giving consideration to span and supersonic aerodynamic performance is characterized in that the head of an aircraft body is in a shape of a long and thin pointed head, the wings are trapezoidal wings with medium sweepback angles, full-motion horizontal tails are symmetrically arranged on two sides of the rear end of the aircraft body, a large sweepback vertical tail is arranged above the rear end of the aircraft body, a rudder is arranged at the rear end of the vertical tail, engine air inlet channels of the aircraft are positioned on two sides of the middle front part of the aircraft body, and an engine cabin of the aircraft is positioned at the tail part of the aircraft body;

wherein the slenderness ratio of the fuselage is 8-11, the sweep angle of the front edge of the wing is 35-45 degrees, the sweep angle of the front edge of the horizontal tail is 35-45 degrees, and the sweep angle of the front edge of the vertical tail is 50-60 degrees.

2. The aircraft of claim 1 wherein the aircraft wing has an arcuate strake inboard of the wing nose.

3. An aircraft having both span and supersonic aerodynamic performance according to claim 1, wherein the front end of the wing of the aircraft is provided with a deflectable motorized flap.

4. The aircraft of claim 1 wherein the rear end of the wing of the aircraft is inboard of a rear flap.

5. An aircraft having both straddle and supersonic aerodynamic performance according to claim 1, wherein the aircraft has ailerons mounted outside the rear end of the wing.

6. The aircraft of claim 1, wherein the missile pylon is mounted outside the wing tip of the wing.

7. The aircraft of claim 1, wherein ventral fins are symmetrically arranged on two sides of a symmetrical plane below the rear end of the aircraft body.

8. The aircraft of claim 1 wherein the aircraft is a single-aircraft.

Technical Field

The invention belongs to the aircraft design technology, and relates to an aircraft layout aircraft with both span and supersonic aerodynamic performance.

Background

The development of a single-engine aircraft which can finish the flight in a large envelope range, has a high transonic lift-drag ratio and can carry out supersonic maneuvering flight is a complex technical task. From the perspective of pneumatic layout, the aircraft is required to realize maximization of lift-drag ratio of transonic speed and supersonic speed on the basis of ensuring subsonic speed controllability, and can meet the requirement of stable control of transverse heading from subsonic speed to supersonic speed. The requirements are mutually contradictory, and the design difficulty of developing the airplane meeting similar conditions is very high.

Disclosure of Invention

The invention aims at a single-engine airplane which is used for flying in a large envelope range and has high transonic lift-drag ratio and supersonic maneuvering flying capability.

The technical scheme of the invention is as follows: an aircraft with both span and supersonic aerodynamic performance is provided, wherein the head of the aircraft body is in a shape of a slender pointed head, the wings are trapezoidal wings with medium sweepback angles, full-motion horizontal tails are symmetrically arranged on two sides of the rear end of the aircraft body, a large sweepback vertical tail is arranged above the rear end of the aircraft body, a rudder is arranged at the rear end of the vertical tail, engine air inlet channels of the aircraft are positioned on two sides of the middle front part of the aircraft body, and an engine cabin of the aircraft is positioned at the tail part of the aircraft body;

wherein the slenderness ratio of the fuselage is 8-11, the sweep angle of the front edge of the wing is 35-45 degrees, the sweep angle of the front edge of the horizontal tail is 35-45 degrees, and the sweep angle of the front edge of the vertical tail is 50-60 degrees.

Preferably, an arched strake wing is installed on the inner side of the front end of the wing of the airplane.

Preferably, the wing nose of the aircraft is fitted with a deflectable motorized flap.

Preferably, the rear end of the wing of the aircraft is inboard mounted with a rear flap.

Preferably, the aircraft is fitted with ailerons outboard of the aft ends of the wings.

Preferably, the missile pylon is mounted outboard of the wing tip.

Preferably, ventral fins are symmetrically arranged on two sides of a symmetrical plane below the rear end of the fuselage.

Preferably, the aircraft is a single-aircraft.

The invention has the advantages that: the aerodynamic layout of the airplane disclosed by the invention realizes the maximization of the lift-drag ratio of transonic speed and supersonic speed on the basis of ensuring the subsonic speed controllability of the airplane, and can also meet the stable control from subsonic speed to supersonic speed in the horizontal course.

Drawings

FIG. 1 is a schematic top view of an aircraft layout designed to compromise transonic aerodynamic performance in accordance with the present invention;

FIG. 2 is a schematic side view of an aircraft layout designed to compromise transonic aerodynamic performance in accordance with the present invention;

fig. 3 is a schematic forward view of an aircraft layout for a cross-supersonic aerodynamic performance compromise aircraft according to the present invention.

In the figure: 1-fuselage, 2-strake, 3-wing, 4-full-motion horizontal tail, 5-vertical tail, 6-engine cabin, 7-rear flap, 8-aileron, 9-wingtip elastic hanging rack, 10-front flap, 11-engine air inlet channel, 12-rudder, 13-ventral fin and 14-aerogun.

Detailed Description

The invention is further illustrated with reference to the following figures and examples.

The aircraft is a normal layout middle single-wing aircraft, and the head of the aircraft body is a slender pointed end, so that the span and supersonic wave resistance can be reduced. The wings of the airplane adopt trapezoidal wings with medium sweepback angles. The full-motion horizontal tails are symmetrically arranged on two sides of the rear end of the airplane body. The pitching control of the airplane is realized by symmetrically deflecting the left horizontal tail and the right horizontal tail. A large sweepback vertical tail is arranged above the rear end of the airplane body of the airplane, so that the course stability of the airplane is provided. And a rudder is arranged at the rear end of the vertical tail, and the yaw control of the airplane is realized through the deflection of the rudder. According to the invention, the ventral fins are symmetrically arranged on two sides below the rear end of the airplane body, so that the course stability of the airplane is improved. According to the invention, the aircraft body is provided with a door of aircraft cannon at the left side below the front part, so that the near combat capability of the aircraft is improved. The air inlet channels of the engine of the airplane are positioned on two sides of the middle front part of the airplane body, so that the high-performance stable operation of the engine in a full-envelope flying state can be ensured. The engine of the airplane is positioned in the engine compartment at the tail part of the airplane body, and provides thrust for the airplane.

The arched strake wing is arranged on the inner side of the front end of the wing of the airplane, so that a high chord length value can be realized at the root of the wing, and the relative thickness of the wing in the area is reduced under the condition that the absolute thickness value of the wing is large. The design can simultaneously reduce the wave resistance across supersonic velocity, increase the fuel oil storage of the wing oil tank and improve the subsonic velocity large-attack-angle maneuvering performance. The front end of the wing of the airplane is provided with a deflectable maneuvering flap. By deflecting the leading flap, sub-transonic cruise and maneuvering performance may be improved. The inner side of the rear end of the wing of the airplane is symmetrically provided with rear flaps. By deflecting the rear flap downwards, the take-off and landing performance can be improved. The outer sides of the rear ends of the wings of the airplane are symmetrically provided with ailerons. The rolling control of the airplane is realized through the differential deflection of the left aileron and the right aileron. The missile hangers are arranged on the outer sides of wingtips on two sides of the wings of the airplane, so that the overload capacity of weapons is improved.

As shown in fig. 1-3, the invention relates to a fuselage 1 of an aircraft with an aircraft layout that allows for cross-supersonic aerodynamic performance. The wings 3 are symmetrically arranged in the middle of the fuselage 1 from left to right, and the edge strips 2 are symmetrically arranged on the inner side of the front end of the wings 3 from left to right. The full-motion horizontal tail 4 is symmetrically arranged at the left and right sides of the rear end of the machine body 1. The vertical fin 5 is installed above the rear end of the body 1. An engine compartment 6 is located at the rear end of the fuselage 1. The rear flaps 7 are arranged on the inner side of the rear end of the wing 3 in a bilateral symmetry manner. The ailerons 8 are arranged on the outer side of the rear end of the wing 3 in a bilateral symmetry way. The wingtip missile hanging racks 9 are symmetrically arranged at the outer sides of the wingtips of the wings 3. The front flaps 10 are arranged at the front ends of the wings 3 in a bilateral symmetry manner. The engine intake ducts 11 are located on both sides of the front part of the fuselage 1. The rudder 12 is located at the rear end of the vertical fin 5. The ventral fins 13 are symmetrically arranged at the left and right sides below the rear end of the fuselage 1. The aircraft cannon 14 is mounted on the lower front left side of the fuselage 1. Wherein the slenderness ratio of the fuselage is 8-11, the sweep angle of the front edge of the wing is 35-45 degrees, the sweep angle of the front edge of the horizontal tail is 35-45 degrees, and the sweep angle of the front edge of the vertical tail is 50-60 degrees.